Mixing characteristics of injector elements in liquid rocket engines - A computational studyA computational study has been performed to better understand the mixing characteristics of liquid rocket injector elements. Variations in injector geometry as well as differences in injector element inlet flow conditions are among the areas examined in the study. Most results involve the nonreactive mixing of gaseous fuel with gaseous oxidizer but preliminary results are included that involve the spray combustion of oxidizer droplets. The purpose of the study is to numerically predict flowfield behavior in individual injector elements to a high degree of accuracy and in doing so to determine how various injector element properties affect the flow.
Document ID
19920071532
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lohr, Jonathan C. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Trinh, Huu P. (NASA Marshall Space Flight Center Huntsville, AL, United States)